Application of a distributed MDAO framework to the design ... · Interface 3/3: systems design •Parametric interfaces between aircraft and systems predesign • Chart 14 th> Application

Application of a distributed MDAO framework to

the design of a short- to medium-range aircraft

www.DLR.de • Chart 1 > Lecture > Author • Document > Date

Erwin Moerland, Thomas Zill, Björn Nagel

Holger Spangenberg, Holger Schumann, Peter Zamov

DLR, Institute of Air Transportation Systems

DLR, Institute of Flight Systems

Contents

www.DLR.de • Chart 2 > Application of a distributed MDAO framework > Erwin Moerland • DLRK2012 > 10th of September 2012

MDO advancing multidisciplinary design & optimisation

Case study design study guiding the integration

System-of-systems approach combining aircraft predesign & design of aircraft systems

Design interfaces coupling both design methods

Initial integration setup aircraft design results, systems design approach

Conclusion conclusive remarks & future challenges

Multidisciplinary Design & Optimisation Definition introduced by Prof. I. Kroo and Prof. J.J. Alonso, Stanford University


1st generation

analysis-based design

computations

• optimisation algorithms

• approximation techniques

COM

COM

Power Equation LP Spool

Power Equ. HP Sp.

HPT Cooling

COM

COM

Power Equation LP Spool

Power Equ. HP Sp.

HPT Cooling

Workflow management

2nd generation

• networked computing

• # disciplinary interfaces

3rd generation

Optimisation assisted

design in teams

• management of knowledge

• collaboration of engineers

and tools

Actors within system-of-systems design approach


Operators • gather resources • establish design teams

OA

D k

now

ledge

●

Workflow

integrators

• setup design workflows • integrate analysis modules

●

System

experts

• provide disciplinary knowledge • generate analysis modules

●

Knowledge detail

www.DLR.de • Chart 5

Common Design

System-

Layout

configuration connection

en

viron

mental

imp

act

En

gin

e in

teg

ration

> Application of a distributed MDAO framework > Erwin Moerland • DLRK2012 > 10th of September 2012

Aircraft redesign for short ranges


1 Source: OAG Aviation - OAG Schedules Data, 2007

payload 190 [pax] 135 [kg]

all economy class with 30‘‘ seat pitch

range 1000 [NM] design range

TOFL 2000 [m] @sea level, MTOW, ISA +15°C

LFL 1500 [m] @sea level, MLW, ISA +15°C

cruise Mach

0.79

span 36 [m] maximum

altitude FL 350 FL 410

initial climb cruise

Nearly 80%: missions with sector length < 1000 [NM] 1

Selection of TLAR for the case study

5

con

v.

6

ou

tpu

t

2 in

itia

lisat

ion

3

anal

ysis

4

syn

th.

1

req

. def

.

syste

ms

pre

lim

inary

des

ign

airc

raft p

relim

ina

ry d

es

ign

source: boeing-727.com

high-lift

concept

final aircraft configuration

(CPACS)

minimum

aircraft

dataset

ParADISE

initialisation

System

boundaries

reference

high-lift

concepts

final systems architecture

(PrEMISE, CATIA)


systems architecture

(PrEMISE)

Top Level Aircraft Requirements (TLAR)

Leve

l 0

Leve

l 1

Leve

l 2

VAMPzero

initialisation

initial aircraft configuration

(CPACS)

Leve

l 0

Leve

l 1

Leve

l 2

Leve

l 3

mass converger feasibility & mass

evaluation

1

req

. def

.

2 in

itia

lisat

ion

3

anal

ysis

4

syn

th.

5

con

v.

6

ou

tpu

t

syste

ms

pre

lim

inary

des

ign

airc

raft p

relim

ina

ry d

es

ign

interface

VAMPzero

initialisation

Loadcase

determination

Aerodynamic polars

Aerodynamic force-

distributions

Engine performance

map

Mission simulation

VAMPzero synthesis

mass converger

high-lift

concept


(CPACS)

minimum

aircraft

dataset

second. struct.

main wing

WINGmass

reitera

te

ParADISE

initialisation

System

boundaries

reference

high-lift

concepts

input files

(tool specific input format)

actuation

safety

kinematics

support structure


(PrEMISE, CATIA)

ParADISE

synthesis

feasibility & mass

evaluation

reitera

te


2

3

1 systems architecture

(PrEMISE)


(CPACS)


Interface 1/3: Data Exchange Format

• Common Parametric Aircraft Configuration Scheme

(CPACS)

• XML based

• <tags>used to build hierarchic structure</tags>:


1 2 3

header

vehicles

missions

airports

fleets

toolspecific

CPACS

aircraft

engine

profiles

struct.elem

materials

composites

vehicles

model 1

model 2

model N

aircraft

name

description

reference

fuselages

wings

engines

ldg. gear

systems

global

analyses

model 1 wings

Pair

wis

e in

tegr

atio

n a

pp

roac

h In

tegrated

data m

od

el app

roach


• Common Parametric Aircraft Configuration Scheme (CPACS) and

Pragmatic Engineering Model for Integrated Systems Engineering

(PrEMISE)


1 2 3

too

l ‚w

rap

pin

g‘

central sp

ecific inp

ut file gen

eration


• Common Parametric Aircraft Configuration Scheme (CPACS) and

Pragmatic Engineering Model for Integrated Systems Engineering

(PrEMISE)


ParADISE

disciplinary tool

disciplinary calculation

convert to tool lang.

convert to PrEMISE

PrEMISE

wrapped disciplinary tool

CPACS

disciplinary calculation

extract

convert to tool lang.

write

convert to CPACS

write input

read output

1 2 3

Decentralised computation framework: RCE for CPACS

Interface 2/3: aircraft design results


Initiation Iterations until convergence

• For a more elaborate discussion on RCE and collaborative data management, please see:

D. Böhnke, Challenges for Collaborative Data Management in an MDAO Process (DLRK2012)

Tools remain on owners‘ servers.

Exchange of input and output in

CPACS format via the network.

1 2 3

http://www.eclipse.org/

Aircraft design

• wing dimensions

• types of moveables and target settings

• secondary wing component: - dimensions - loads - weights

Level 0 Level 1 Level 2

Interface 2/3: aircraft design

• Parametric interfaces between aircraft and systems predesign


1 2 3

CPACS geometry

Interface 3/3: systems design

• Parametric interfaces between aircraft and systems predesign


1 2 3

Systems design

• high-lift concept feasibility

• high-lift support structure: - locations - dimensions

• system properties: - weight - costs - power budget

1

req

. def

.

2 in

itia

lisat

ion

3

anal

ysis

4

syn

th.

5

con

v.

6

ou

tpu

t

syste

ms

pre

lim

inary

des

ign

airc

raft p

relim

ina

ry d

es

ign

interface

VAMPzero

initialisation

Loadcase

determination

Aerodynamic polars

Aerodynamic force-

distributions

Engine performance

map

Mission simulation

VAMPzero synthesis

mass converger

high-lift

concept


(CPACS)

minimum

aircraft

dataset

second. struct.

main wing

WINGmass

reitera

te

ParADISE

initialisation

System

boundaries

reference

high-lift

concepts

input files

(tool specific input format)

actuation

safety

kinematics

support structure


(PrEMISE, CATIA)

ParADISE

synthesis

feasibility & mass

evaluation

reitera

te


2

3

1 systems architecture

(PrEMISE)


(CPACS)


Conclusion


• System-of-systems approach in preliminary design

• Proper disciplinary interfacing techniques

• Integration frameworks

Large potential for increasing OAD knowledge

in predesign phases

• Challenges

• Technical: connecting disciplinary analysis tools

• Non-technical: establishing effective

communication

more research focus on the organisational

level of MDO

Collaborative Design in the Integrated Design Lab


Documents

Application of a distributed MDAO framework to the design ... · Interface 3/3: systems design •Parametric interfaces between aircraft and systems predesign • Chart 14 th> Application